Gas turbine system with a transition duct having axially extending cooling channels
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United States of America Patent
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Dec 12, 2017
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app pub date -
Aug 15, 2014
filing date -
Aug 15, 2014
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Abstract
A gas turbine system (1) including a burner arrangement having a tubular combustion chamber (5), a turbine (6) and a transition duct (7) connecting the combustion chamber (5) and the turbine (6), wherein the transition duct (7) is provided with an axially extending cooling air channel (11). The transition duct (7) includes a plurality of axially extending cooling air channels, and wherein each cooling air channel (11) is provided with one single inlet (12) opened to the outside of the transition duct (7) and with one single outlet (12) opened to the inside of the transition duct (7).
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